Abstract: An accessory gear box for a gas turbine engine having a drive shaft with a rotational axis and a tower shaft coupled to the drive shaft is provided. The accessory gear box includes a first plurality of gears arranged, which extend along a first axis substantially parallel to the rotational axis of the drive shaft. The accessory gear box includes a second plurality of gears, which extend along a second axis. The accessory gear box includes a first shaft, with one of the first plurality of gears coupled to the first shaft, and one of the second plurality of gears coupled to a second shaft. The one of the second plurality of gears coupled to the first shaft includes a first engagement surface and a second engagement surface, and the second engagement surface is coupled to another one of the second plurality of gears to drive the second shaft.

Abstract: Embodiments of a turboshaft engine are provided, as are embodiments of a method for manufacturing a turboshaft engine. In one embodiment, the turboshaft engine includes an Inlet Particle Separator (IPS) system having an IPS scavenge flow circuit fluidly coupled to the engine's inlet section. A heat exchanger and a heat exchanger bypass duct are fluidly coupled to the IPS scavenge flow circuit. The heat exchanger bypass duct is configured to direct airflow around the heat exchanger. A particle separation device, such as an IPS blower, is fluidly coupled in series with the heat exchanger in the IPS scavenge flow circuit. The particle separation device is positioned to direct particulate matter entrained within the airflow through the IPS scavenge flow circuit into an inlet of the heat exchanger bypass duct and thereby reduce the amount of particulate matter ingested by the heat exchanger during operation of the turboshaft engine.

Abstract: An accessory gear box for a gas turbine engine having a drive shaft with a rotational axis and a tower shaft coupled to the drive shaft is provided. The accessory gear box includes a first plurality of gears arranged, which extend along a first axis substantially parallel to the rotational axis of the drive shaft. The accessory gear box includes a second plurality of gears, which extend along a second axis. The accessory gear box includes a first shaft, with one of the first plurality of gears coupled to the first shaft, and one of the second plurality of gears coupled to a second shaft. The one of the second plurality of gears coupled to the first shaft includes a first engagement surface and a second engagement surface, and the second engagement surface is coupled to another one of the second plurality of gears to drive the second shaft.

Abstract: A gas turbine engine and an accessory gear box (AGB) are provided for. The gas turbine engine comprises a drive shaft, a compressor, a combustor and an exhaust turbine, where the exhaust turbine and the compressor are coaxially connected by the drive shaft. The gas turbine engine further comprises an engine casing of varying diameters circumferentially enveloping the compressor, the combustor and the exhaust turbine with a waist located between the compressor and the combustor. The gas turbine engine also includes an accessory gear box (AGB) attached to the engine casing at the waist, the AGB comprising a gear rotating on an axis extending in a transverse direction relative to that of the drive shaft.

Abstract: Embodiments of a turboshaft engine are provided, as are embodiments of a method for manufacturing a turboshaft engine. In one embodiment, the turboshaft engine includes an Inlet Particle Separator (IPS) system having an IPS scavenge flow circuit fluidly coupled to the engine's inlet section. A heat exchanger and a heat exchanger bypass duct are fluidly coupled to the IPS scavenge flow circuit. The heat exchanger bypass duct is configured to direct airflow around the heat exchanger. A particle separation device, such as an IPS blower, is fluidly coupled in series with the heat exchanger in the IPS scavenge flow circuit. The particle separation device is positioned to direct particulate matter entrained within the airflow through the IPS scavenge flow circuit into an inlet of the heat exchanger bypass duct and thereby reduce the amount of particulate matter ingested by the heat exchanger during operation of the turboshaft engine.

Abstract: A gas turbine engine and an accessory gear box (AGB) are provided for. The gas turbine engine comprises a drive shaft, a compressor, a combustor and an exhaust turbine, where the exhaust turbine and the compressor are coaxially connected by the drive shaft. The gas turbine engine further comprises an engine casing of varying diameters circumferentially enveloping the compressor, the combustor and the exhaust turbine with a waist located between the compressor and the combustor. The gas turbine engine also includes an accessory gear box (AGB) attached to the engine casing at the waist, the AGB comprising a gear rotating on an axis extending in a transverse direction relative to that of the drive shaft.

Abstract: An inlet door system including an aft inlet duct mounted door actuator providing RAM air to an auxiliary power unit (APU) contained within an aircraft is provided. The inlet door system includes an inlet duct, the aft inlet duct mounted door actuator, and a door. The inlet duct is configured to extend from the auxiliary power unit to the aircraft housing and has a sidewall that defines a flow passage. The door actuator is mounted to an exterior surface of the aft portion of the inlet duct. The door is coupled to the actuator. The actuator is configured to selectively rotate the door between at least a first position and a second position.

Abstract: An inflatable sealing assembly for sealing between an intake section of a turbine engine and an air inlet ring of a vehicle. The inflatable sealing assembly including a seal holder coupled to the intake section of the engine and having a first inflatable seal, a second inflatable seal, and a closed cell foam material disposed therein. The first inflatable seal and the second inflatable seal are configured when inflated to provide a seal between the intake section of the turbine engine and the air inlet ring of the vehicle and prevent foreign object debris and/or water from entering the turbine engine.

Abstract: A cooling system is provided for an engine of a rotorcraft configured to generate a downwash into an atmosphere during operation. The system includes an inlet coupled to the engine and configured to receive a liquid from the engine; an outlet coupled to the engine and configured to return the liquid to the engine; and a body defining a conduit having a first end coupled to the inlet and a second end coupled to the outlet such that the liquid flows from the inlet to the outlet through the conduit and transfers heat to the atmosphere via the downwash from the rotorcraft.

Abstract: An inflatable sealing assembly for sealing between an intake section of a turbine engine and an air inlet ring of a vehicle. The inflatable sealing assembly including a seal holder coupled to the intake section of the engine and having a first inflatable seal, a second inflatable seal, and a closed cell foam material disposed therein. The first inflatable seal and the second inflatable seal are configured when inflated to provide a seal between the intake section of the turbine engine and the air inlet ring of the vehicle and prevent foreign object debris and/or water from entering the turbine engine.

Abstract: An inlet door system including an aft inlet duct mounted door actuator providing RAM air to an auxiliary power unit (APU) contained within an aircraft is provided. The inlet door system includes an inlet duct, the aft inlet duct mounted door actuator, and a door. The inlet duct is configured to extend from the auxiliary power unit to the aircraft housing and has a sidewall that defines a flow passage. The door actuator is mounted to an exterior surface of the aft portion of the inlet duct. The door is coupled to the actuator. The actuator is configured to selectively rotate the door between at least a first position and a second position.

Abstract: A method and apparatus for cooling the heat generated by a gas turbine engine mounted in a compartment is provided. The apparatus comprises a novel eductor that incorporates a mixer nozzle to entrain sufficient air flow through the compartment to provide all the necessary cooling. The engine's oil cooler is mounted to the eductor so that the entrained air flow passes through it and cools the engine's oil. The novel eductor also has means for receiving a flow of high velocity air from the engine and injecting this air downstream of the mixer nozzle to enhance the entraining of the cooling flow.

Abstract: A radial inflow particle separator includes a pair of axially and radially spaced curvilinear walls cooperatively defining a circumferential flow path leading radially inwardly and axially to an engine. Preferably, the particle separator is employed with a turbine engine which is operated at times in an environment laden with dust and particulate matter. Such an environment is typically encountered by a turbine engine of a helicopter, or off-road vehicle. The particle separator provides dust and particulate control features including aero-inertial, particle trajectory, particle boundary-rebound, and scavenge flow tailoring to achieve a dust and particulate separation efficiency as good as or better than the best conventional axial-flow particle separators. This particle separation effectiveness is achieved in a radial inflow particle separator which is smaller and lighter in weight than axial flow devices, and which packages advantageously with the essential structures of a turbine engine.